CN103737069B - The method for designing of cutter and its cutter for drilling composite element - Google Patents
The method for designing of cutter and its cutter for drilling composite element Download PDFInfo
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- CN103737069B CN103737069B CN201310662112.9A CN201310662112A CN103737069B CN 103737069 B CN103737069 B CN 103737069B CN 201310662112 A CN201310662112 A CN 201310662112A CN 103737069 B CN103737069 B CN 103737069B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23B—TURNING; BORING
- B23B51/00—Tools for drilling machines
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Abstract
The method for designing of a kind of drilling cutters, described cutter at least includes that higher level's drill bit with predetermined diameter and diameter are more than subordinate's drill bit of predetermined diameter, and described method includes: according to Fa=2A×10‑1.089γ(f/2)0.5G1Calculate the drilling thrust of cutter, according toCalculate layers of material critical thrust, according to Fa≤FTCalculating cutter parameters, wherein, described cutter parameters includes anterior angle γ of cutter main sword outer radius, drift angle 2 ε of cutter, the chisel edge width 2w of cutter and diameter 2b, 2c of cutter;And design cutter according to calculated cutter parameters.
Description
Technical field
The present invention relates to a kind of cutter for drilling composite element method for designing and
The cutter designed by the method, particularly relates to a kind of at composite element, especially at carbon
Process hole on fibre-reinforced composite element, especially process the design of the cutter of large diameter hole
Method and the cutter designed by the method.
Background technology
Carbon fiber has the most excellent mechanical property and mechanical performance, tool compared with other materials
Having higher specific strength and specific modulus, carbon fiber has height as the reinforcing material in composite
The features such as intensity high-modulus and high fragility, resin then has low-intensity, low as matrix material
The feature such as modulus and good toughness.The fighter plane of military service, its machine is entered in the world after the eighties
The wing, empennage parts use carbon fibre composite mostly.The USAF being on active service in 2005
Newest F-22 " bird of prey " fighter plane, composite accounts for 35%, in the middle of aircraft skin wallboard, wing
Beam, fuselage bulkhead, hatch door and miscellaneous part etc. all have employed carbon fibre composite.The U.S.
Armed helicopter RAH-66, again can high-performance cruise after VTOL, tilting rotor
V-22 " osprey ", composite consumption reaches the 50% of construction weight.B787 fuselage agent structure
Using composite, application percentage reaches the 50% of whole machine weight;The rear of A380, wing,
Central authorities' wing box, pressure bulkhead, fixed fin and horizontal stabilizer etc. use composite structure,
Application percentage reaches 32%;The application of A350 composite is similar with B787, and application percentage reaches
52%.The rear of C series aircraft, wing, central authorities' wing box, pressure bulkhead, vertical fin and horizontal tail
Deng employing composite structure, application percentage reaches 37%.The composite of some light aerocrafts
Application percentage is more up to more than 90%, even occurs in that full composite material aircraft.Composite
The ratio of application has become as weighs one of advanced important symbol of aircraft.
In the extensively application of carbon fibre composite, secondary mechanical processing is more and more, especially
It is when composite material parts is with other parts assembly connections, large number of orifices to be carried out
Processing.Such as one frame F-16 fighter plane has 40,000 connecting holes, a frame Boeing-747 aircraft to have
More than 300 ten thousand connecting holes.Drilling becomes in composite material parts manufacture course of products workload
Heavy machining operation, the F-22 fighter plane of United States advanced will be compound in development process
Material boring puts forward as a key technology.The efficient drilling of composite is present generation aircraft system
Make one of industry most critical technology.It is reported, in external aircraft assembling process, because Drilling operation lacks
Fall into and cause the carbon fibre composite number of parts scrapped account for the 60% of whole faulty part with
On.China has the composite consumption of the airliner C919 of entirely autonomous intellectual property will
Reach 15~23%, it may be said that current advanced composite structure proportion number, at certain
The important technology index evaluating aeroplane performance has been become in the degree of kind.
Carbon fibre composite is due to anisotropy and intensity height, big, the poor thermal conductivity of hardness etc.
Feature so that it causes tool wear serious when hole machined, tool life is low and hole lacks
Fall into the phenomenons such as serious.
And traditional bore process can not meet the requirement of large diameter hole processing, the present invention relates to
And a kind of for composite strengthen composite large diameter hole processing dedicated tool.Due to carbon
Fibre reinforced composites are high by the soft and tough resin material of matter and intensity, hardness is big
Two-phase that fibre reinforced materials mixes or heterogeneous structure, its mechanical property is anisotropy,
Interlayer contact intensity is low, easily produces serious processing in working angles under the effect of cutting force
Defect, generally, in the composite drilling process of more than 9mm large diameter hole,
As easy as rolling off a log generation layering and tear etc., greatly destroy the intensity of composite laminated plate;Big straight
The course of processing in hole, footpath to go through brill reaming multiple working procedure, and production efficiency is low.Therefore composite wood
In the material large diameter hole course of processing, how to design cutter so that the aperture precision processed is high,
Become a great problem to be solved.
About the patent of carbon fibre composite aperture knife tool, number of patent application is
201310047795.7 patent disclose the carbon fibre reinforced composite of a kind of braze-welded structure
Special diamond drill bit, feature is on cutter hub sidewall to have to consider clearly hole to be worth doing, at the head of cutter hub
Connecting drill bit, drill bit is with one group of notch.Number of patent application is the patent of 201220148618.9
Disclosing carbon fibre composite and titanium alloy spiral hole milling dedicated tool, feature is bit
Portion and cervical region are stepped, and the cutting head at cutter neck is peripherally evenly arranged with four all side millings
Tooth.Number of patent application be 201220592135.8 patent disclose a kind of processing fibre reinforced
Composite and the drill bit of titanium alloy laminated plate, feature is that the drill point angle in apex point portion is three drift angles
Arrange.The common ground that above patent exists is all without reference to processing large diameter hole
Cutter, simply emphasizes single processing mode, it is impossible to complete the disposable processing of large diameter hole.
Summary of the invention
The present invention provides the method for designing of a kind of cutter for drilling composite element, especially
Provide a kind of at composite element, especially at carbon fiber reinforced composite element
Upper processing hole, the especially method for designing of the cutter of large diameter hole.
The composite that the present invention solves in drilling process within composite element easily divides
The technical problem of layer.Overcome composite element especially carbon fiber reinforced composite structure
Hole (especially large diameter hole) the unmanageable technical problem of part, and improve working (machining) efficiency.
Present invention overcomes the shortcoming that processing hole especially large diameter hole needs much knives to have, carry
Supply a kind of drilling cutters, it is possible to achieve disposably complete the whole course of processing, reach simultaneously
Preferably hole surface quality.For realizing this purpose, the technical solution of the present invention is to set up
Drill bit drill thrust model, is layered critical force model in conjunction with drill bit, by ensureing drill thrust less than facing
Boundary's layering drill thrust realizes parameter designing and the optimization of drilling.
According to above-mentioned purpose, devise the side of a kind of cutter for drilling composite element
Method, wherein, described cutter at least includes higher level's drill bit and extends continuously also from described higher level's drill bit
And its diameter is more than subordinate's drill bit of described higher level's drill bit, described method is designed under described
Level drill bit starts drilling thrust during drilling and is less than or equal to layers of material critical thrust.Specifically
Ground, described method includes:
-according to Fa=2A×10-1.089γ(f/2)0.5G1Calculate the drilling thrust of cutter, wherein, described
The radius of higher level's drill bit is scheduled, and A is constant, before the cutter main sword outer radius that γ is predetermined
Angle, f is the feed rate of predetermined cutter;
Wherein,ψ is chisel edge and horizontal angle, 2 ε of predetermined cutter
For the drift angle of predetermined cutter, 2w is the chisel edge width of predetermined cutter, and R is subordinate to be asked
The radius of drill bit, D is the diameter of subordinate's drill bit to be asked;
-basis Calculate material
Layering critical thrust, wherein,κ=b/c, in above-mentioned relation formula, b represents
The radius of described higher level's drill bit, it is scheduled as previously mentioned, and c represents the half of described subordinate drill bit
Footpath, its value is R value, and E represents the elastic modelling quantity of described composite element, and v represents institute
Stating the Poisson's ratio of composite element, h represents the non-cutting layer thickness of described composite element,
Herein, the thickness of last layer of laying of described composite element, G can be takenICExpression is faced
Limiting fissure stricture of vagina propagation energy, wherein, E, v, h and GICIt is known quantity;
-according to Fa≤FTCalculate the radius c of described subordinate drill bit.
-come according to the radius of predetermined higher level's drill bit and the radius c of calculated subordinate drill bit
Design cutter.
According to another aspect of the present invention, disclose a kind of for drilling composite element
Cutter, it obtains according to previous designs method.
For two-stage drilling cutters, described tool body section includes the boring for boring
Section and from described boring section along the axial direction of described cutter continue to extend for reaming
Reaming section, wherein, when carrying out reaming, described boring section is considered higher level's drill bit, described expansion
Hole section is considered subordinate's drill bit.
For three grades of drilling cutters, described tool body section includes the boring for boring
Section, the expansion for reaming extended along the continuation of the axial direction of described cutter from described boring section
Hole section and from described reaming section along the axial direction of described cutter continue extend be used for ream
Fraising section, wherein, when carrying out reaming, described boring section is considered higher level's drill bit, described
Reaming section is considered subordinate's drill bit, and when reaming, described reaming section is considered higher level's drill bit,
Described fraising section is considered subordinate's drill bit.
For more stages drilling cutters, described tool body section includes the brill for boring
Hole section, from described boring section along the axial direction of described cutter continue to extend for expanding step by step
Multiple reaming sections in hole and continue to extend from described reaming section along the axial direction of described cutter
For fraising fraising section, wherein, when carrying out first order reaming, described boring section is regarded
For higher level's drill bit, described first reaming section is considered subordinate's drill bit, when reaming, and institute
Stating last reaming section and be considered higher level's drill bit, described fraising section is considered subordinate's drill bit, when
When carrying out reaming with middle reaming section, place reaming section is considered subordinate's drill bit, with place
The upper reaming section that reaming section is adjacent is considered higher level's drill bit
Preferably, described boring section has fluted drill Double-margin structure.
Preferably, described reaming section has staged straight groove structure.
Preferably, described fraising section has spiral cut reamer structure.
Preferably, described boring section has rake face and rear knife face, and uses gash angle to remove chisel edge
Technology.
Accompanying drawing explanation
In order to explain the present invention, its illustrative embodiments be will be described below with reference,
In accompanying drawing:
Fig. 1 is the design flow diagram of the present invention;
Fig. 2 (a) is the cutting layer thickness Parameter Map of drill bit;
Fig. 2 (b) is the apex point geometrical morphology figure of drill bit;
Fig. 3 is the cutting experiment device schematic diagram of one embodiment of the present invention;
Fig. 4 is the partial enlarged drawing of Fig. 3.
Similar features in different figures is by similar reference instruction.
Detailed description of the invention
Step drill class drilling cutters may be considered multistage drill bit and combines.Here, this kind of cutter
Tool can include two-stage drilling cutters, three grades of drilling cutters and more stages drilling cutters.For two
Level drilling cutters for, including act on be boring higher level's drill bit and effect be that reaming is also
And subordinate's drill bit that diameter is bigger.For three grades of drilling tools, it is boring including effect
And higher level's drill bit of diameter minimum, effect are that the subordinate of fraising and diameter maximum bores
Head and effect are reaming and the diameter middle bit between the above two, wherein, are somebody's turn to do
Middle bit can be considered subordinate's drill bit for reaming, for fraising can be considered on
Level drill bit.For more stages drilling tool, it is that boring and diameter are minimum including effect
Higher level's drill bit, effect is fraising and the maximum subordinate's drill bit of diameter and acts on
Big middle bit and is become between the above two step by step, wherein when will be with in reaming and diameter
For certain special diameter reaming, the middle bit with this special diameter can be considered subordinate's brill
Head, the middle bit adjacent less than this special diameter can be considered higher level's drill bit.
When crackle starts to expand, boundary's thrust of step drill occurs to start drilling at subordinate's drill bit
Time.
See Fig. 1, Fig. 2 (a) and Fig. 2 (b), (all to composite element with drilling cutters
The sheet material made such as carbon fiber reinforced composite) in drilling process, every on drill edge
Drilling thrust at Yi Dian can represent with following formula.
Fa=2A×10-1.089γ(f/2)0.5G1
Wherein, A × 10-1.089γ=Kn, A is constant, by tool geometrical parameter and cutting parameter institute
Determine, KnFor the energy coefficient of the vertical stress component on Tool in Cutting sword, γ is cutter main sword external diameter
The anterior angle at place, f is the feed rate of cutter.Wherein, higher level's drill bit of γ, f and cutter
Radius can be made a reservation in advance.
Further, in above-mentioned formula,
Whereinψ is chisel edge and horizontal angle, and 2 ε are cutter drift angle, 2w
For the chisel edge width of cutter, R is the radius of subordinate's drill bit, and D is the diameter of subordinate's drill bit, its
Middle D=2R.Wherein, ψ, 2 ε, 2w are all made a reservation in advance, and the value of R and/or D is waited to solve.
Yet further, drilling thrust institute work, strain energy and the cracks can spread of drill bit
Can mathematical relationship may refer to following relational expression:
Relational expression (1) can represent unstable stratification state, and relational expression (2) can represent
Critical stratification state, relational expression (3) can represent non-stratification state.More specifically, Δ U
Representing strain energy differential, dA represents the increment of hierarchical crack area, GICList in intermediate scheme I
Critical condition of crack extension energy on plane is long-pending, X represents displacement.
Theoretical according to Plate Theory and bent beam, and public affairs during the most critical stratification state of combination
Formula, can be critical thrust F in the hope of drilling thrust produced during critical stratification stateT。
Wherein,κ=b/c, in above-mentioned relation formula, b represents the radius of higher level's drill bit,
I.e., being scheduled, c represents the radius of the subordinate drill bit adjacent with aforesaid higher level's drill bit,
As it was previously stated, its value is R value, E represents the elastic modelling quantity of composite element to be drilled,
V represents the Poisson's ratio of composite element to be drilled, and h represents not cutting of composite element
Layer thickness (here it is possible to taking the thickness of last layer of laying of composite element), GICTable
Show critical condition of crack extension energy.In aforementioned formula, E, v, h, GICIt is known quantity, c
It is worth and waits to solve.
Generally believe that carbon fiber reinforced composite (CFRP) adds in drilling and there is material man-hour
Material layering critical thrust value (FT), therefore, in drilling process, in order to ensure carbon fiber reinforced
The defects such as layering are not produced, it shall be guaranteed that drill bit is executed in drilling process inside composite element
The drilling axial force added is less than layers of material critical thrust value.In other words, little when drilling axial force
In or equal to layers of material critical thrust value (Fa≤FT) time, drilling process will not occur point
Layer damage phenomenon.
Drill thrust model and critical thrust model are substituted into formula Fa≤FTIn (such as following formula), can
In the hope of the relational expression of layers of material critical thrust of tool geometrical parameter and the cutter of step drill,
And then foundation and guidance can be provided for the design of tool geometrical parameter.
According to inequality above, the c value solving out is a numerical range, generally for cutting
Cut efficiency and can choose maximum.And, if the cutter being designed is the drilling exceeding two-stage
Cutter, then can continue to calculate radius and/or the diameter of subordinate's drill bit, in turn, calculate complete.
The method according to the invention can design a kind of cutter for drilling composite element,
This cutter carry out including the two-stage drilling process of drilling and reaming or include boring, reaming and
The three grades of drilling process reamed or the more stages drilling behaviour including boring, multistage reaming and fraising
Make.
In order at composite element, particularly carbon fiber reinforced composite element is (general
For sheet material) on process the whole hole of special diameter, cutter can be designed according to preceding method.Under
The embodiment in face be according to preceding method design can be at carbon fiber reinforced composite panel
The cutter in the whole hole of a diameter of 9.54mm is processed on material.
In embodiment as shown in Figure 3 and Figure 4, three grades of drilling cutters of this brill reaming include cutter
Tool main part 1 and shank portion 2.
Specifically, tool body section 1 has boring section 3, reaming section 4 and fraising section 5,
Boring section 3 has fluted drill Double-margin structure, is suitable for processing carbon fiber reinforced composite structure
Part, reaming section 4 has staged straight groove structure, and fraising section 5 has spiral cut reamer structure.
Wherein, in time wanting reaming, boring section 3 is considered as higher level's drill bit, and reaming section 4 is considered as subordinate and bores
Head;Wait time to be reamed, reaming section 4 is considered as higher level's drill bit, and fraising section 5 is considered as subordinate's drill bit.
More specifically, boring section 3 has rake face and rear knife face, and gash angle is used to remove chisel edge
Technology, it is possible to axial force is dramatically reduced, reduces carbon fiber reinforced composite hole machined
Time layering and the defect such as splitting.
In this embodiment, the fluted drill diameter of movement of boring section 3 is designed to 3.26mm,
According to Fa=2A×10-1.089γ(f/2)0.5G1Calculate drilling thrust produced by cutter reaming section 4, its
In2 ε are that the drift angle of cutter takes 118 °;γ is outside the main sword of cutter
Anterior angle at footpath, takes 25 °;F is that the feed rate of cutter takes 0.02mm/rev;ψ is cutter
Chisel edge and horizontal angle take 50 °;2w is that the chisel edge width of cutter takes 0.1mm;So,
FaIt is the function expanding cutter tool radius R.It addition, according to Calculating layers of material is critical
Thrust, wherein,What κ=b/c, h represented composite element does not cuts thickness
Degree (here it is possible to taking the thickness of last layer of laying of composite element), when reaming
B represents that the radius 1.63mm, c of described higher level's drill bit (boring section) represents described subordinate drill bit
The radius of (reaming section).Above-mentioned numerical value is substituted into Fa≤FTI.e. can calculate the cutter of reaming section
Tool radius.In like manner, the reamer radius of fraising section 5 can be calculated.That is: reaming section 4
Reamer diameter of movement is designed to 5.0mm, 7.9mm and 9.5mm successively, and allowance depends on
Secondary for 1.74mm, 2.9mm and 1.6mm;The reamer diameter of movement of fraising section 5 is 9.54mm
(requiring to be consistent with whole bore dia), processing She's amount is 0.04mm.This allowance distribution and cutter
The design of angle meets actual drill thrust in formula and is less than the requirement of critical layering thrust so that bore
Without lamination during cutting.
The cutter of the present invention uses the drift angle of 118 °, 18 °~the helical angle of 28 °, it is ensured that
The apex point intensity of cutter, improves cutting-tool's used life.The boring section 3 of tool body section 1
After drilling bore hole, follow-up reaming section 4 and fraising section 5 can repair carbon fiber reinforced further
The burr that composite produces, it is ensured that the precision in hole and crudy.
The cutter of the present invention uses CVD coating technology on hard alloy substrate, improves cutter
Service life, coating layer thickness is 1 μm~3 μm.
Three grades of drilling cutters of the present embodiment use and once bore reaming, without tool changing, by original four
The workload that five cutters can complete concentrates on a cutter, greatly reduces workload,
Provide working (machining) efficiency significantly.
The cutter of previous embodiment can process the whole Kong Bingneng of a diameter of 9.54mm and obtain relatively
Good hole machined quality is owing to this cutter can disposably complete the processing of large diameter hole, permissible
It is greatly improved production efficiency during big aircraft drilling.
The cutter of the method according to the invention design, owing to combining the analysis of mathematical model, will face
Boundary's thrust model introduces in the design of cutter so that the axial force produced during hole machined is less than
Produce the critical thrust of layering, thus substantially reduce carbon fiber reinforced composite hole machined
Time defect, improve the crudy in hole.
Above-mentioned cutter is applicable to machining composite material, particularly the plate of carbon fibre reinforced composite
Material, when boring section machined parameters is n=6000rpm, f=0.006mm/rev, reaming section processing ginseng
Number is n=800rpm, f=0.02mm/rev, and fraising section machined parameters is n=500rpm,
During f=0.02mm/rev, surface roughness Ra < 3.2 μm, the table of gateway, hole in processing hole
Without layering at the basic zero defect of face pattern, and ultrasonic scanning Microscopy Results fiber outlet
Occur.
The present invention is not in any way limited to the exemplary reality presented in the specification and illustrated in the drawings
Execute mode.All combinations of the embodiment (part) illustrated and describe are clearly understood that
For within being incorporated to this description and be clearly understood that as falling within the scope of the present invention.And,
In the scope of the present invention that such as claims are summarized, many variations is possible.Additionally,
Any reference marker in claims should be constructed as limiting the scope of the present invention.
Claims (9)
1. being used for a method for designing for the cutter of drilling composite element, described cutter is at least
Including higher level's drill bit with extend continuously from described higher level's drill bit and its diameter is more than described higher level
Subordinate's drill bit of drill bit, described method for designing is designed to when described subordinate drill bit starts drilling
Drilling axial force is less than or equal to layers of material critical thrust, and described method includes:
-according to Fa=2A × 10-1.089γ(f/2)0.5G1Calculate the drilling thrust of cutter, wherein, described
The radius of higher level's drill bit is scheduled, wherein, and A × 10-1.089γ=Kn, A is constant, by cutter geometry
Parameter and cutting parameter are determined, KnFor the energy coefficient of the vertical stress component on Tool in Cutting sword,
The anterior angle of the cutter main sword outer radius that γ is predetermined, f is the feed rate of predetermined cutter;Wherein,ψ is
The chisel edge of predetermined cutter and horizontal angle, 2 ε are the drift angle of predetermined cutter, and 2w is pre-
The chisel edge width of fixed cutter, R is the radius of subordinate's drill bit to be asked, D be to be asked under
The diameter of level drill bit;
-basisCalculate material
Layering critical thrust, wherein,κ=b/c, in above-mentioned relation formula, b represents
The radius of described higher level's drill bit, it is scheduled as previously mentioned, and c represents the half of described subordinate drill bit
Footpath, its value is R value, and E represents the elastic modelling quantity of described composite element, and v represents institute
Stating the Poisson's ratio of composite element, h represents the non-cutting layer thickness of described composite element,
GICRepresent critical condition of crack extension energy, wherein, E, v, h and GICIt is known quantity;
-according to Fa≤FTCalculate the radius c of described subordinate drill bit;And
-come according to the radius of predetermined higher level's drill bit and the radius c of calculated subordinate drill bit
Design cutter.
2., for a cutter for drilling composite element, it is according to setting as claimed in claim 1
Meter method obtains, and it includes tool body section and shank portion.
Cutter the most according to claim 2, it is characterised in that described tool body section includes
For the boring section holed and continue to prolong from described boring section along the axial direction of described cutter
The reaming section for reaming stretched, wherein, when carrying out reaming, on described boring section is considered
Level drill bit, described reaming section is considered subordinate's drill bit.
Cutter the most according to claim 2, it is characterised in that described tool body section includes
For the boring section of boring, continue to extend from described boring section along the axial direction of described cutter
The reaming section for reaming and from described reaming section along the axial direction of described cutter continue
The fraising section for fraising extended, wherein, when carrying out reaming, described boring section is considered
Higher level's drill bit, described reaming section is considered subordinate's drill bit, when reaming, described reaming section
Being considered higher level's drill bit, described fraising section is considered subordinate's drill bit.
Cutter the most according to claim 2, it is characterised in that described tool body section includes
For the boring section of boring, continue to extend from described boring section along the axial direction of described cutter
The multiple reaming sections for reaming step by step and from axial along described cutter of described reaming section
The fraising section for fraising extended, wherein, when carrying out first order reaming, institute are continued in direction
Stating boring section and be considered higher level's drill bit, described first reaming section is considered subordinate's drill bit, when entering
During row fraising, last reaming section described is considered higher level's drill bit, and described fraising section is considered
Subordinate's drill bit, when carrying out reaming with middle reaming section, place reaming section is considered subordinate and bores
Head, a upper reaming section adjacent with the reaming section at place is considered higher level's drill bit.
6. according to the cutter described in claim 4 or 5, it is characterised in that described boring section has fiber crops
Flower bores Double-margin structure.
7. according to the cutter described in claim 4 or 5, it is characterised in that described reaming section has rank
Ladder type straight groove structure.
8. according to the cutter described in claim 4 or 5, it is characterised in that described fraising section has spiral shell
Spin slot reamer structure.
Cutter the most according to claim 6, it is characterised in that described boring section has rake face
With rear knife face, and gash angle is used to go chisel edge technology.
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CN107832546B (en) * | 2017-11-24 | 2019-12-03 | 西北工业大学 | A kind of prediction technique and system of laminated construction drilling axial force |
CN108733912B (en) * | 2018-05-17 | 2021-08-03 | 南京理工大学 | Method for predicting height of burrs at outlet of robot rotary ultrasonic drilling CFRP/aluminum alloy laminated structure |
CN108952597B (en) * | 2018-07-24 | 2020-12-04 | 邹城兖矿泰德工贸有限公司 | Special anti-impact drill rod |
CN110757263B (en) * | 2019-11-07 | 2021-01-29 | 中国工程物理研究院机械制造工艺研究所 | Mechanical grinding method-based micro-opening control method for micro-arc-edge diamond cutter |
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